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Orbital Quarterly News Volume 20, Issues 1 & 2 April 2016 Recent NOAA-16 Breakup Inside... In late November 2015, the decommissioned synchronous , where it operated until replaced Debris History of NOAA- U.S. NOAA-16 (International and transferred to backup status in 2005. An Series Spacecraft 2 Designator 2000-055A, U.S. Strategic Command anomaly abruptly ended communication with the [USSTRATCOM] Space Surveillance Network satellite on 6 June 2014, and it was decommissioned Fragmentation of [SSN] catalog number 26536) experienced a on 9 June 2014. Upper Stage Debris 2 breakup event, resulting in a substantial debris The breakup occurred at approximately -M Core Stage cloud. The 1475 kg dry mass satellite was launched 0950 GMT on 25 November 2015. At the time, the Fragments Near 21 September 2000, as part of the Polar Operational spacecraft was in an 841 x 857 km orbit. The Joint GEO Orbit 3 Environmental Satellite (POES) series of U.S. Space Operations Center (JSpOC) has now catalogued weather . It was placed into a 98.9° sun- 136 objects, making it a rather large breakup. The Briz-M Core Stage Fragments in figure below Elliptical Orbit 4 is a composite Gabbard plot, Russian SOZ Unit which shows a Breaks Up in March 4 classic pattern. As with previous The 2016 UN COPUOS STSC Meeting 5 NOAA breakups, much of the ORDEM 3.0 V&V debris will remain Document Available 5 in orbit for many decades in what Top Ten Satellite Breakups is already a very Reevaluated 5 crowded altitude. There is no ORDEM 3.0 indication that V&V Findings 7 the breakup was anything other Conference Report 10 than an explosion, Space Missions & possibly due to a Sat Box Score 12-13 battery failure. ♦

Dispersion of debris from the NOAA-16 breakup of 136 tracked debris (including the parent body). The Gabbard plot shows the classic “X” pattern indicative of an explosive breakup from a circular orbit.

Note: All requests for information on the recent Astro H (Hitomi) A publication of event are being directed to JAXA, the Japan Aerospace eXploration Agency. the NASA Orbital Debris Program Office Orbital Debris Quarterly News

A Debris History of the NOAA-Series Spacecraft

The U.S. National Oceanographic and Atmospheric the three generations of NOAA spacecraft have provided regular Administration (NOAA) eponymous spacecraft have provided weather data since the launch of NOAA 1 in 1970. NOAA’s third global weather data as the low orbit (LEO) component of generation spacecraft, NOAA 1-5, were succeeded in service by the the integrated weather data service. As a follow-on to the first two more sophisticated fourth and fifth generations built around the generations of Television InfraRed Observation Satellites (TIROS), TIROS-N and Advanced TIROS-N (ATN) busses. Whereas the third generation vehicles resided in sun-synchronous NOAA International Launch ISS Solid around 1500 km altitude, later vehicles were launched into SSN # Common Name Spacecraft Bus Type Designator Date Rocket Motor Generation lower-inclination orbits around 833 and 870 km altitude. 1970 - 106 4793 NOAA 1 (ITOS-A) DEC 70 3 TIROS-M x The table provides the flight log for these spacecraft. 1972 - 082 6235 NOAA 2 (ITOS-D) OCT 72 3 TIROS-M x The NASA Orbital Debris Program Office (ODPO) 1973 - 086 6920 NOAA 3 (ITOS F) NOV 73 3 TIROS-M x recognizes several types of debris-generating events. 1974 - 089 7529 NOAA 4 (ITOS G) NOV 74 3 TIROS-M x These include standard breakups and anomalous events. 1976 - 077 9057 NOAA 5 (ITOS H) JUL 76 3 TIROS-M x 1979 - 057 11416 NOAA 6 (NOAA A) JUN 79 4 TIROS-N -37S Breakups are the usually destructive disassociation of an 1980 - 043 11819 NOAA B MAY 80 4 TIROS-N STAR-37S orbital object, typically characterized by large separation 1981 - 059 12553 NOAA 7 (NOAA C) JUN 81 4 TIROS-N STAR-37S velocities for the resulting fragments. Anomalous events 1983 - 022 13923 NOAA 8 (NOAA E) MAR 83 4 ATN STAR-37S 1984 - 123 15427 NOAA 9 (NOAA F) DEC 84 4 ATN STAR-37S are the unplanned separation of one or more objects from 1986 - 073 16969 NOAA 10 (NOAA G) SEP 86 4 ATN STAR-37S an essentially intact body, usually at a low velocity; these 1988 - 089 19531 NOAA 11 (NOAA H) SEP 88 4 ATN STAR-37S events may reflect the effects of the on 1991 - 032 21263 NOAA 12 (NOAA D) MAY 91 4 TIROS-N STAR-37S the parent object. 1993 - 050 22739 NOAA 13 (NOAA I) AUG 93 4 ATN STAR-37S NOAA 6, 7, 8, 10, 11, 12, and 14 have experienced 1994 - 089 23455 NOAA 14 (NOAA J) DEC 94 4 ATN STAR-37S 1998 - 030 25338 NOAA 15 (NOAA K) MAY 98 5 ATN STAR-37XFP anomalous events over their operational and post-mission 2000 - 055 26536 NOAA 16 (NOAA L) SEP 00 5 ATN STAR-37XFP lifetimes. NOAA 8 also experienced a breakup event 2002 - 032 27453 NOAA 17 (NOAA M) JUN 02 5 ATN STAR-37XFP on 30 December 1985, believed to have been caused by 2005 - 018 28654 NOAA 18 (NOAA N) MAY 05 5 ATN x a battery explosion. None of these events, however, 2009 - 005 33591 NOAA 19 (NOAA N') FEB 09 5 ATN x TIROS: Television IR Observation Satellite ITOS: Improved TIROS Operational System were as dramatic as the November 2015 explosion of ATN: Advanced TIROS-N NOAA 16. ♦ ISS: Integrated Stage System

Fragmentation of Fregat Upper Stage Debris A debris object associated with the launch (International Designator 2011-037B, U.S. reside in an elliptical deep space orbit similar to of ’s Spektr-R radio astronomy satellite Strategic Command [USSTRATCOM] Space the payload and is apparently uncataloged. The fragmented on 3-4 August 2015. The object Surveillance Network [SSN] catalog number fragmented object is most likely the separable 37756) is described fuel/oxidizer tank discarded by the Fregat upper in the SSN catalog stage between its early and later burns. Low‐thrust engines as SL-23 DEB, one The Fregat-SB is based on the of five debris objects Fregat upper stage but adds a toroidal hypergolic cataloged with this fuel/oxidizer tank, the sbrasyvaemye blok bakov launch. Four of the (SBB) and is variously referred to as the Main tank block debris objects, piece jettisoned tanks unit (JTU) or block (JTB), as tags C, E, F, and G, shown in Fig. 1. The tank accommodates two are likely the launch fuel and two oxidizer tanks, isolated by spherical Jettisoned vehicle second stage’s bulkheads; unfortunately, at this writing, it is tank block solid rocket motor not clear if these are common bulkheads, as separation caps, and employed in the design of the similar Briz-M are typically observed upper stage’s auxiliary propellant tank. The JTU Ignition support with launches of the uses high pressure helium bottles to pressurize system SL-23/-3SLBF the tanks and devices to sever attachment and variant . cabling to the Fregat upper stage body, perhaps Main engine Circumstances of this indicative of failure modes. mission’s launch profile Figure 2 provides another view of the Figure 1. A perspective view of the Fregat-SB upper stage. The suffix “SB” indicates the Fregat sbrasyvaemye baki or “jettisonable tanks” variant. Source: imply that the upper Ref. 1. stage, a Fregat-SB, may continued on page 3

2 www.orbitaldebris.jsc..gov Fragmentation continued from page 2 The JTU structure basis of the Phobos-Grunt propulsion module/ is welded aluminum alloy cruise stage. AMg6 [2] while bulkheads are constructed of AD1 and AMg6 References alloys. Overall dimensions of 1. User’s Guide/Rev. B, the toroid are 0.821-m height Space International Services, (1 October 2014). (tank diameter) and an overall 2. Anon. “Propulsion System for diameter of 3.440 m. Dry mass Delivering “Phobos-Grunt” Spacecraft on is quoted as 340-375 kg [3, 4, Phobos Surface”, p. 186. Accessed from ftp:// 5]. The fuel is unsymmetrical naif.jpl.nasa.gov February 2016. dimethylhydrazine (UDMH) 3. Zenit-3SLBV ILV/Zenit-M SRC while the oxidizer is nitrogen User’s Guide, Center for Ground Space

tetroxide (N 2O 4). These Infrastructure Operations (TsENKI), (June hypergolic components can 2011). explode on contact, indicating a 4. Asyuchkin, V.A. and S.V. Ishin. possible failure mode. “Multipurpose Upper Stage “Fregat-SB” with Figure 2. The separated JTU. This unit, used by the Phobos-Grunt The event, of unknown Enhanced Power Capacity”, Solar System spacecraft, is assumed identical to the standard JTU. The actual JTU cause, produced a total of Research 46, no. 7, pp. 519-22 (December was likely covered with insulation blankets. Source: Ref. 2. 24 debris. As of 3 April 2016 2012). Russian-language manuscript originally none had entered the SSN published in Vestnik, no. 1, pp. 9-12, (2011). separated tank, revealing the He pressure catalog. Three Fregat-SB upper stages have been 5. Ilin, A. “Fobos-Grunt”, Novosti and stage equipment and systems more launched, and a fourth, modified, provided the Kosmonavtiki, vol. , no. 1, p. 35, (January clearly. 22 2012). ♦

Briz-M Core Stage Fragments Near The Briz-M upper stage associated with the launch of Russia’s Cosmos 2513 Additional fuel tank (AFT) Central fuel tank satellite fragmented on 16 January 2016 Upper stage (US) at approximately 03:50 GMT. The object Fairing lower adapter (International Designator 2015-075B, U.S. Helium pressurization Strategic Command [USSTRATCOM] Space sphere balloon (conventionally revolved) Surveillance Network [SSN] catalog number Equipment bay 41122) consists of the core body of the Briz-M Oxidizer high upper stage, the separable Auxiliary Propellant pressure tank Tank having been jettisoned in the elliptical transfer orbit. At the time of the event the object had been on-orbit about 33 days and was Oxidizer high at an altitude of approximately 34866 km over a pressure tank subsatellite point of 0.17°S, 223°E. The general layout is depicted in lateral cross-section by Fig. 1. The cylindrical core is 2.49 m in diameter and 2.654 m in overall Fuel high pressure tank length, excluding the payload adapter, and is estimated to have a dry mass of 1220 kg. Up to 10 pieces have been observed. Adapter system/ However, as of 3 April 2016, no debris had upper stage (US) interface officially entered the SSN catalog. Debris in Fairing separation plane deep space orbits are difficult for the SSN to US/launch vehicle (LV) separation plane track and catalog. Potentially there could be AFT separation plane hundreds of additional fragments. US/LV technological As new GEO fragmentations present a interface plane rare opportunity, the Orbital Debris Program Figure 1. A lateral cross section of the Briz-M stage, including the jettisonable Auxiliary Propellant Tank. continued on page 4 Source: Ref. 1. All dimensions are in millimeters.

3 Orbital Debris Quarterly News Briz-M Explosion continued from page 3

Office staff mobilized its assets in an attempt to observe the new debris cloud at an early stage of its evolution. NASA’s Standard Satellite Breakup Model was used to create a model debris cloud of fragments ≥ 10 cm in characteristic length. The resulting cloud was then propagated forward in time and projected against the celestial sphere, as shown in Fig. 2. The NASA/Air Force Research Lab Meter- Class Autonomous Telescope (MCAT) has successfully observed objects in the high density areas predicted by the model. A confirmation that the observed objects are indeed correlated with this debris cloud, either by statistical inference or the propagation of SSN cataloged debris (when available), remains to be done.

Reference 1. International Launch Services. Launch System Mission Planner’s Guide/Rev. 7 (July 2009): A-6. ♦

A plot of the density of debris produced by the NASA modeled debris cloud against the celestial sphere as the cloud orbits during 2 days during January 2016. Yellow areas represent the regions of greatest spatial density, the so-called “pinch point” and its antipodal “pinch line.” The white dots are the background stars with the two vertical bands being the galactic plane.

Briz-M Core Stage Fragments in Elliptical Orbit The Briz-M upper stage associated with the sequence. At the time of the event the object As of 3 April 2016, eight debris had launch of Canada’s Nimiq 6 communications had been on-orbit 3.6 years and was in a 12° officially entered the SSN catalog in addition satellite fragmented on 23 December 2015 inclination, 34592 by 10408 km orbit. Based on to the parent object. All debris are in orbits at approximately 16:00 GMT. The object the nominal breakup time, the event occurred at similar to the parent object, with a maximum (International Designator 2012-026B, U.S. an altitude of approximately 24310 km over a change in period of 13.9 minutes and change Strategic Command [USSTRATCOM] Space subsatellite point of 11.9°N, 178°E. in inclination of 0.09°. Debris in deep space Surveillance Network [SSN] catalog number Readers are referred to this issue’s orbits are difficult for the SSN to track and 38343) consists of the core body of the Briz-M article “Briz-M Core Stage Fragments Near catalog. Hundreds of additional fragments upper stage, the separable Auxiliary Propellant Geosynchronous Orbit” for the general layout could be on-orbit. ♦ Tank having been jettisoned earlier in the launch and physical characteristics of the stage.

Russian SOZ Unit Breaks Up in March A Sistema Obespecheniya Zapuska (SOZ) restart, are routinely ejected after the Block DM an SL-12 Auxiliary motor, fragmented into ullage motor from a Proton Block DM fourth stage ignites for the final time; they also provide at least 21 pieces. The motor was in a highly stage broke up at approximately 12:12 GMT three-axis control to the Block DM during elliptical 18840 x 682 km orbit at an inclination on 26 March 2016. These motors have a long coast. This SOZ unit (International Designator of 65.36° at the time of the breakup. Given history of fragmentations. This event is the 2008-067G, SSN# 33472) is associated with the difficulties in tracking objects in elliptical and 44th breakup of this class of object over its launch of the Cosmos 2447-2449, members deep space orbits, there could be many more history and the first since 2014 (ODQN, vol. 18, of the Russian global positioning navigation fragments on orbit. ♦ issue 4, October 2014, pp. 1-2). Ullage motors, system, GLONASS, constellation. used to settle propellants prior to an engine The unit, also commonly referred to as

4 www.orbitaldebris.jsc.nasa.gov The 2016 UN COPUOS STSC Meeting The United Nations (UN) Committee on and Research Updates;” “The IADC: An more than 10 informal consultation meetings the Peaceful Uses of (COPUOS) Overview of the IADC Annual Activities;” on the margins to continue work on developing Scientific and Technical Subcommittee (STSC) “OneWeb;” “Overview of - the draft guidelines. The WG Chair proposed held its annual meeting (the 53rd session) at the Related Activities in France in 2015;” “Recent a “phased approach” that would have allowed Vienna International Center during February Developments of the International Scientific for adoption of an initial set of guidelines in 15-26, 2016. Seventy of the 83 Member States Optical Network (ISON) Project;” “ 2016 and development of a second tranche of were represented at the 53rd session, and 38 Practices on Satellites Post Mission Disposals guidelines in 2017-2018. Although the U.S. other nations or organizations attended the Toward Space Long Term Sustainability;” and and nearly all other COPUOS Member States session as observers. Among other topics, the “Space Debris Mitigation Activities at ESA in agreed with this phased approach, ultimately session’s agenda items included Space Debris, 2015.” All presentations are available at the UN it did not achieve consensus during the STSC , Global Navigation Satellite COPUOS website: http://www.unoosa.org/ session. The WG also did not reach consensus Systems, Near-Earth Objects, and the Long- oosa/en/ourwork/copuos/stsc/technical- on a draft report to document the activities of Term Sustainability of Outer Space Activities presentations.html#stsc2016. the WG conducted during the STSC session. (LTS). Established in 2010, the LTS Working The current mandate for the LTS WG will Many Member States expressed concern at Group (WG) has made significant progress expire at the end of the June 2016 COPUOS the challenges presented by space debris. The developing a consensus report with voluntary meeting. The LTS WG did agree to hold a two- U.S. statement on Space Debris emphasized the best-practice guidelines that, if endorsed, could day intersessional meeting immediately before importance of the UN Space Debris Mitigation be implemented by States to help ensure the safe the June 2016 COPUOS meeting in hopes of Guidelines and called on all space-faring and sustainable use of outer space for peaceful reaching a consensus on the initial set of draft nations and organizations to implement these purposes, for the benefit of all countries. The guidelines. As the U.S. National UN Guidelines to limit the generation of space U.S. and many other COPUOS Member States notes, “the U.S. calls on all nations to work debris. Several technical presentations were have played an active role in the development together to adopt approaches for responsible provided during the session, including “United of the LTS guidelines since that time. The LTS activity in space to preserve this right for the States Space Debris Environment, Operations, WG held 8 meetings in the STSC plenary and benefit of future generations.” ♦

ORDEM 3.0 Verification and Validation Document Available The NASA technical publication Earth orbiting population, and V&V outcomes nasa.gov/collections/TRS/_techrep/TP- “NASA Orbital Debris Engineering Model for both the spacecraft and telescope modes 2015-218592.pdf. Those wishing to obtain ORDEM 3.0 – Verification and Validation” of operation. Interested readers are directed the ORDEM 3.0 model and its attendant document (NASA/TP-2015-218592, October to this issue’s project review “ORDEM 3.0 User’s Guide may request a copy at http:// 2015) is now available to the public. This Verification and Validation Findings” for a orbitaldebris.jsc.nasa.gov/model/engrmodel. document reviews the verification and summary of several key determinations and html. ♦ validation (V&V) process, how it was applied may obtain a copy from the Johnson Space to the ORDEM 3.0 computer model of the Center Technical Report Server at ston.jsc.

PROJECT REVIEW Top Ten Satellite Breakups Reevaluated

P. ANZ-MEADOR developments since the previous publication of 14, issues 2 and 4, April and October 2010; vol. Between the beginning of the Space Age “Top Ten Satellite Breakups” (ODQN, vol. 14, 16, issue 3, July 2012; and issue 1 of volumes on 4 October 1957 and 1 January 2016, more issue 3, July 2010, pp. 2-3). 17, 18, and 19, January 2013, 2014, and 2015, than 5160 space missions have been conducted By far the source of the greatest amount respectively). worldwide. Of the over 40,000 objects of orbital debris remains the -1C This satellite alone now accounts for cataloged by the U.S. Space Surveillance spacecraft, which was the target of a People’s 3428 cataloged fragments or almost 20% of Network (SSN), 17,255 are on-orbit and are Republic of China anti-satellite test in January the entire population of cataloged manmade traveling independently as of the latter date. 2007 (see previous ODQN articles: vol. 11, objects in orbit about the planet. Additional However, only 10 missions now account for issues 2 and 3, April and July 2007; vol. 12, debris from this test and other events are approximately one-third of all cataloged objects issues 2 and 3, January, April, and July 2008; vol. currently being tracked by the SSN and are now in Earth orbit. In this article we review 13, issues 1 and 3, January and July 2009; vol. continued on page 6

5 Orbital Debris Quarterly News Top Ten Satellite Breakups continued from page 5 officially cataloged on a routine basis. now in eighth place in the list due to on-going better illustrates the long-term environmental The second and fourth most significant cataloging of the cloud. hazard posed by historical events. The reader satellite breakups are Cosmos 2251 and Not listed in Table 1 is the breakup of the should note that up to six of the events listed spacecraft, which were involved in Briz-M upper stage (International Designator in Table 2 would have been potentially obviated the first ever accidental impact 2006-006B, SSN# 28944) which broke-up into by modern U.S. and international mitigation of intact objects in February 2009. While over an estimated 1,000+ fragments in February 2007 practices. 68% of the Cosmos debris cloud remains on (ODQN, vol. 11, issue 2, April 2007, pg. 3). Half of Table 1’s top 10 are replaced in orbit, only 58% of the Iridium cloud is on orbit, However, the highly elliptical of the Table 2 by older events, though Fengyun-1C, due in part to the higher area-to-mass ratio bias stage’s orbit (~500 km by nearly 15,000 km) has Cosmos 2251, and Iridium 33 debris clouds of the latter cloud. Because of their relatively impeded the SSN’s ability to detect, to identify, retain their primacy. Table 2’s new entries have high altitude, these clouds will continue to and to catalog the associated debris. As of as their signal attribute a higher altitude of present a hazard for decades to come. January 2016, 102 debris from the Briz-M breakup. Indeed, four of the five reside in sun- Conversely, the relatively high area-to- stage had been officially cataloged, of which 94 synchronous orbits over 1000 km in breakup mass ratio distribution of the STEP 2 rocket remain on-orbit. altitude. The fifth, the Cosmos 2227 SL-16/Zenit body’s debris cloud, the third most significant While Table 1 allows the reader to rocket body, is massive at an estimated dry mass event, and the low altitude of the Cosmos 2421 adduce the effectiveness of international of 8.9 metric tons, and experienced multiple event, the fifth most significant, have resulted debris mitigation policies and guidelines over breakup events. All members of this list will in a minimal long-term environmental hazard. the course of the past decades, another way continue to pose a hazard to for Only about 11% of the former, and none to examine the consequences of historical decades to come. Furthermore, many reside in of the latter remain on-orbit at this time. breakup events is presented in Table 2. In popular low Earth orbits and pose an enhanced Otherwise, only the order of the top 10 events this table, the total number of debris on-orbit risk to other spacecraft due to their inclinations has changed as the former tenth place entry, is regarded as the figure of merit in lieu of and attendant relative velocity. ♦ the CBERS 1/SACI 1 CZ-4 rocket body is Table 1’s total number of debris cataloged. This

Table 1. Top 10 Breakups, January 2016

International Year of Altitude of Cataloged Debris in Assessed Cause Rank Common Name Designator Breakup Breakup Debris Orbit of Breakup 1 1999 25 Fengyun-1C 2007 850 3428 2880 intentional collision 2 1993 36 Cosmos 2251 2009 790 1668 1141 accidental collision 3 1994 29 STEP-2 Rocket Body 1996 625 754 84 accidental explosion 4 1997 51 Iridium 33 2009 790 628 364 accidental collision 5 2006 26 Cosmos 2421 2008 410 509 0 unknown 6 1986 19 SPOT-1 Rocket Body 1986 805 498 32 accidental explosion 7 1965 82 OV2-1 / LCS 2 Rocket Body 1965 740 473 33 accidental explosion 8 1999 57 CBERS 1 / SACI 1 Rocket Body 2000 740 431 210 accidental explosion 9 1970 25 Nimbus 4 Rocket Body 1970 1075 376 235 accidental explosion 10 2001 49 TES Rocket Body 2001 670 372 80 accidental explosion * as of 04 January 2016 9137 5059

Table 2. Number of Debris in Orbit, January 2016

International Year of Altitude of Assessed Cause Rank Common Name In Orbit* Total Designator Breakup Breakup of Breakup 1 1999 25 Fengyun-1C 2007 850 2880 3428 intentional collision 2 1993 36 Cosmos 2251 2009 790 1141 1668 accidental collision 3 1997 51 Iridium 33 2009 790 364 628 accidental collision 4 1981 53 Cosmos 1275 1981 980 289 346 battery explosion 5 1970 25 Nimbus 4 Rocket Body 1970 1075 235 376 accidental explosion 6 1999 57 CBERS 1 / SACI 1 Rocket Body 2000 740 210 431 accidental explosion 7 1992 93 Cosmos 2227 Rocket Body # 1992 830 199 279 accidental explosion 8 1975 52 Nimbus 6 Rocket Body 1991 1090 199 274 accidental explosion 9 1973 86 NOAA 3 Rocket Body 1973 1515 179 201 accidental explosion 10 1976 77 NOAA 5 Rocket Body 1977 1510 174 184 accidental explosion * as of 04 January 2016 5870 7815 # multiple events associated with this SL-16 Zenit second stage

6 www.orbitaldebris.jsc.nasa.gov ORDEM 3.0 Verification and Validation Findings M. MATNEY, P. KRISKO, A. VAVRIN, AND [1]. This article highlights two sections of the analysis verification of the spacecraft P. ANZ-MEADOR the ORDEM 3.0 V&V document – analysis mode. Note that these satellites are chosen As is the case with any computer model verification of spacecraft mode and testing from six different regions – LEO (low), LEO purporting to accurately describe a physical validation for LEO and GEO populations. (high), Middle Earth Orbit (MEO), Molniya, process, the model should be subject to Geosynchronous Transfer Orbit (GTO), and scrutiny and an enlightened skepticism until Analysis Verification GEO. Though not elaborated upon further in that model has been through a thorough Because many of the algorithms used to this article, the ORDEM telescope mode was verification and validation (V&V) evaluation. compute fluxes in ORDEM 3.0 are unique, also verified using four test cases; this mode The NASA Orbital Debris Engineering Model verifying them presented a special challenge. is applicable to any pencil beam-type ground- (ORDEM) version 3.0 models the Earth Several independent codes were created based sensor. Two cases simulated Haystack orbital environment of man-made debris for specifically for the V&V process that use observations at (Azimuth, Elevation) those larger than 10 µm in size residing in different sets of assumptions and algorithms combinations of (90°, 75°) and (180°, 10°); a (LEO) and 10 cm and larger to compute the same or similar flux values as generic vertically-starring equatorial sensor; in geosynchronous orbit (GEO) from 2010 to the ORDEM software. These special codes and the Meter-Class Autonomous Telescope 2035. Prior to its release, ORDEM 3.0 was are slower and can take many hours to run (MCAT) located at at an subjected to a systematic V&V process and, as compared to the corresponding ORDEM orientation of (0°, 80°). is reported in this issue’s news, a NASA report codes. documenting this process and the outcomes The legacy NASA Orbital Debris Program Spacecraft Mode Example has been released and is now available to the Office (ODPO) programs – GEO_KESSLER_ Figures 1, 2, and 3 are examples of analysis public. IGLOO and LEO_KESSLER_IGLOO – verification charts for a LEO orbit; in this The purpose of the V&V document is to were modified to use the ORDEM populations case, the Tropical Rainfall Measuring Mission ensure that: to compute fluxes sorted by direction and (TRMM) spacecraft orbit (International • the model is built correctly: velocity and to handle special orbits with fixed Designator 1997-074A, USSTRATCOM SSN verification; and nodes, specifically for spacecraft cases. These catalog number 25036, in a 397-km circular “Kessler” models use variants of Kessler’s orbit, inclination 35°). These plots are • the correct model was built: spatial density formulation [2]. The reason typical of LEO orbits, where the ORDEM validation. why a separate program is required for LEO fluxes match those computed by Kessler to The complete V&V process generally and GEO is due to the differences in how the high fidelity. Figure 1 shows the normalized encompasses the entire software lifecycle, and orbital elements of the populations are binned distribution in relative velocity and Figure 2 is therefore a task from inception to retirement. in the ORDEM model. The programs LEO_ shows the normalized distribution in yaw angle The process for ORDEM 3.0 borrows from KESSLER_TELE and GEO_KESSLER_ of the flux. In both cases, the lines for the the Institute of Electrical and Electronics TELE use the same spatial density subroutines different models are indistinguishable on the Engineers (IEEE) in IEEE Std. 1012-1998 to compute fluxes for the telescope cases. The graphs. Figure 3 shows the sample data points and includes standard verification activities generic term “Kessler” refers to the results of taken from the ORDEM 3.0 and Kessler (analysis, testing, inspection, demonstration) any of these runs. and validation activities (analysis and testing) Six satellite test cases were used during continued on page 8

Figure 1. TRMM, Year 2014, Random Argument of Perigee (AP), debris flux Figure 2. TRMM, Year 2014, Random AP, debris flux (normalized) distributed (normalized) distributed over relative velocity bins, ORDEM 3.0 vs. Kessler. over yaw bins, ORDEM 3.0 vs. Kessler.

7 Orbital Debris Quarterly News ORDEM 3.0 V&V continued from page 7 bin-by-bin flux distributions (the igloo flux Scaled Flux Deviations vs. Altitude in LEO specifically exclude Sodium-Potassium is divided into direction and relative velocity One set of metrics discussed in the (NaK) reactor coolant droplets deposited bins), supplemented with a best-fit line, ORDEM 3.0 V&V document is scaled on-orbit by the ’s Radar Ocean 95% confidence interval (CI), and the 95% flux deviations vs. altitude of LEO model Reconnaissance satellites (RORSATs) during prediction interval (PI). An ideal match would populations. The > 3.16 cm and > 1 cm model end of mission operations. The special NaK fall along the 1:1 line, which this example does, populations currently used in ORDEM 3.0 are populations are modeled separately due to except for the very small flux values where the statistically estimated from available Haystack their particular spherical shape. In addition, contributions are the smallest. This example (pointing directions 75°E [90° azimuth, there are some specific families of populations illustrates no statistically significant difference 75° elevation] or 20°S [180°, 20°]) and HAX that are not included in the LEGEND source between ORDEM 3.0 and independent (pointing direction 75°E) staring-mode data, populations and are modeled separately with a computer codes and therefore is considered to using the ODPO LEO to GEO Environment distinct approach. fully meet the intent of the verification process. Debris (LEGEND) source models as the Each validation test includes two charts: a scaled flux deviation Ƀ vs. altitude chart; a Testing Validation initial population estimate. The population estimation is based on observed and predicted probability distribution function (pdf) Validation is provided through the radar detection probability distributions in the histogram supplemented with a normal curve systematic comparison of model populations two-dimensional space of radar range and fit – ܰሺߥǡ ߪሻ using a fitted mean ν; and a pdf and environmental in situ and remotely- range-rate. Due to the statistical nature of the histogram supplemented with a normal curve sensed measurements. The validation of the limited radar samplings, the model populations fit of 1-sigma ܰ Ƀҧǡͳ . Figure 4 shows the Ƀ vs. ORDEM 3.0 modeled debris populations, in are obtained as an average over all the detailed altitude for Haystack 75°E pointing direction terms of the original NASA measurements, aspects such as altitudes, year, different radar for years 1999 to 2003 for > 1 cm. has been a high-priority effort for several viewing geometries, etc. This weighted average The dots represent observational data points ҧ years during the development of ORDEM. model parameter is a weighted average over and the “unweighted” average Ƀ and weighted ෰ It has culminated in techniques and sets of different data sets (i.e., of different year and average Ƀ are portrayed as lines. Figure 5 metrics that were chosen by the developers with different radar viewing geometry) based shows the probability distribution function to validate the model. Simply put, a study on the variances that include the dispersion (pdf) histogram of Ƀ (solid black line) for matrix that includes the parameters of parameter, which is a measure of the deviation Haystack 75°E pointing direction, 1999-2003, debris size, altitude, and year, the measured of data from the assumption of pure Poisson > 1 cm. This distribution is overlapped by a environments of available sensors (Goldstone, statistics. In this regard, the observed OD normal curve fit – ܰሺߥǡ ߪሻ (solid blue line). ҧ Haystack, the Haystack Auxiliary [HAX] fluxes are supposed to be randomly distributed Notice the fitted meanν is very close to Ƀ . The ҧ radar, and the Space Surveillance Network), around model predicted “mean” values. This “unweighted” average Ƀ is represented as a and in-situ measurements are compared to has been tested, specifically for the deviations dashed red line. Figure 6 includes the same pdf the ORDEM 3.0 modeled environments. of radar-observed OD fluxes from ORDEM histogram as before, but with a different curve Comparisons of this kind are limited to those model predictions. fit – ܰ Ƀҧǡͳ . This example is considered to regions of space and time where measurements The radar data used in the model fully meet the intent of the validation process. are available and have been analyzed. population estimations continued on page 9

Figure 3. TRMM, Year 2014, Random AP, bin-by-bin debris flux comparison, Figure 4. Haystack 75°E, >1 cm, altitude over scaled flux deviations. ORDEM 3.0 vs. Kessler.

8 www.orbitaldebris.jsc.nasa.gov ORDEM 3.0 V&V continued from page 8

GEO Population Validation Example MODEST absolute magnitude is derived from [USSTRATCOM SSN catalog number 10365]). Validation of ORDEM 3.0 in GEO is the MODEST instrumental magnitude. The No attempt has been made to identify challenging due to a lack of available data. While ODPO converts absolute magnitude to size the origin of any fragments in the MODEST the LEO SSN Catalog reliably tracks objects by assuming that each object is a Lambertian database. It was discovered after the ORDEM down to about 10 cm, and the Goldstone/ sphere with an albedo of 0.13. The process 3.0 software release that the Titan 3-C Haystack/HAX sensor set contributes over is inverted to derive absolute magnitude fragments were counted twice, once 1,000 hours per year of statistical data to from size. Absolute magnitude and size are without identification in the MODEST and a minimum size of about 3 mm, the GEO inversely related. Bright/large objects have extended MODEST database and again in the regions must depend on the SSN Catalog low magnitudes, while dim/small objects have LEGEND fragmentation deposit. This results (~ > 1 m) and the GEO survey data provided larger magnitudes. The cutoff of the 20th in a 10% population error that will be rectified by the ODPO-sponsored Michigan Orbital absolute magnitude corresponds to 10 cm in in the next ORDEM release. Debris Survey Telescope (MODEST). The size, the smallest size calculated in the GEO The histograms in Figures 7 and 8 display dataset. This is shown in Figures 7 and 8. the ORDEM 3.0 GEO population at the For the purposes of end of 2006 in terms of number vs. absolute ORDEM 3.0 GEO magnitude and number vs. size, respectively. development, the The individual curves represent source ODPO considers the components. The cataloged objects (in red) MODEST survey to include the complete set of cataloged objects in be complete down to GEO. MODEST data does include fortuitous 30 cm. Observations surveyed observations of cataloged objects, but support the hypo- the survey is intended to be statistical, where thesis that the multiple observations are handled by estimating historical period and correcting for the observation biases. For has experienced these reasons, the MODEST cataloged data is a number of excluded from the ORDEM 3.0 GEO objects, unobserved relying instead on the more complete catalog explosive breakups and LEGEND database data. in GEO other Uncataloged objects in blue are MODEST than the two observations (> 30 cm). For the construction acknowledged events of the ORDEM 3.0 populations, these objects (Titan 3-C Transtage are weighted by their observation probability. [USSTRATCOM The drop-off in detections beginning at Figure 5. Haystack 75°E, >1 cm, pdf histogram of scaled flux deviations, SSN catalog number overlayed with normal fit curve. 3432] and Ekran 2 continued on page 10

Figure 6. Haystack (75°E), > 1 cm, pdf histogram of scaled flux deviations, Figure 7. ORDEM 3.0 GEO file for 2006, absolute magnitude (bins = 0.5). overlayed with normal fit curve of 1-sigma.

9 Orbital Debris Quarterly News ORDEM 3.0 V&V continued from page 9 around 17th absolute magnitude (~25 cm) is observation data based on the NASA breakup breakup events in the LEGEND process. The a function of the limiting magnitude of the model. Uncataloged objects in green are number of these objects continues to increase MODEST system as object size decreases. derived from LEGEND for the two known with decreasing size, as shown in Figure 8. The Uncataloged objects in magenta represent an breakups in GEO. These are the fragments ODPO software development team considers extension (30 cm to 10 cm) of the MODEST (> 10 cm) that are distributed from statistical the ORDEM 3.0 GEO environment to be validated to 10 cm characteristic sizes.

Conclusion ORDEM 3.0 has been subject to extensive verification and validation by the ODPO software development team. The results of the validation activities used all available data. These findings correctly and completely represent the ORDEM 3.0 model specifications and requirements defined by NASA.

References 1. Anon., IEEE Computer Society. “IEEE Standard for Software Verification and Validation,” IEEE Standard 1012-1998, 20 July 1998. 2. Kessler D.J. “Derivation of the Collision Probability between Orbiting Objects: The Lifetimes of Jupiter’s Outer Moons,” Icarus, vol. 48, p. 39-48 (Oct. 1981). ♦

Figure 8. ORDEM 3.0 GEO file for 2006.

CONFERENCE REPORT The 66th International Astronautical Congress (IAC), 12-16 October 2015, Jerusalem, Israel

The 66th International Astronautical experiments, long-term environment modeling, addition, a special presentation by OneWeb for Congress (IAC) was held 12-16 October hypervelocity impact testing and simulations, an overview of their planned 720 spacecraft 2015 in Jerusalem. Like the previous IACs, mitigation and remediation, as well as concepts constellation in LEO was arranged by the the Space Debris Symposium during the IAC and technology development for active debris symposium coordinators. All participants was organized by the International Academy removal. In total, 70 oral and 33 interactive were highly impressed by OneWeb’s proactive of Astronautics (IAA). The Space Debris presentations were given during the Space approach to address potential orbital debris Symposium consisted of nine oral sessions, Debris Symposium, making it one of the most issues associated with their constellation. If including one joint session with the Space active symposiums of the 2015 IAC. implemented as planned, OneWeb’s debris Security Committee, one virtual forum with The two best attended debris sessions, mitigation effort to protect the near-Earth young professionals, and one interactive with more than 100 participants overall, were space environment would serve as a good presentation session. The interactive session “Space Debris Removal Technologies” and model for others to follow. ♦ was a new format that replaced the traditional “Space Debris Removal Concepts” sessions. poster sessions. The 10 debris sessions covered Highlights for the two sessions include updates a wide range of activities, including ground- on debris capture mechanisms, such as robotic based radar and telescope observations, space- arms and nets, and several planned active based in-situ measurements, laboratory-based debris removal demonstration missions. In

10 www.orbitaldebris.jsc.nasa.gov

UPCOMING MEETINGS 20-22 April 2016: 13th Annual CubeSat Developer's Workshop, San Luis Obispo, California (USA) This workshop continues the annual University. For updates and more information http://www.cubesat.org/index.php/ series hosted by the California Polytechnic please refer to the CubeSat Project website: workshops/upcoming-workshops.

18-20 May 2016: 8th International Association for the Advancement of Space Safety (IAASS) Conference, Melbourne, Florida (USA) In cooperation with the International remediation, re-entry safety, probabilistic for Commercial , and Space Safety Foundation (ISSF), the IAASS risk assessment, space situational awareness Human Performance and Safety on Long will host its 8th conference, themed “Safety (SSA) and space traffic control, and launch Duration Missions. For more information First, Safety for All.” Among the conference’s and in-orbit collision risk. In addition to please refer to the conference website: topics of interest to this readership are conference sessions, a set of panel sessions http://iaass.space-safety.org/. designing safety into space vehicles, safety will address Space Debris Reentry Safety, of extravehicular activities, space debris , Safety Standards 6-8 June 2016: 4th International Workshop on Space Debris Modeling and Remediation, , France CNES HQ will host the fourth associated with modeling small satellites associated technologies, and economics. workshop in this series. The workshop will and constellations, and debris remediation. Please contact Organizing Committee include oral and poster sessions on space Remediation topics include policy, planning, Chair Mr. Christophe Bonnal, Christophe. debris modeling, including uncertainties system studies, remediation concepts and bonnal@.fr, for further information.

30 July - 7 August 2016: 41st Committee on Space Research (COSPAR) 2016, Istanbul, Turkey The 41st Committee on Space program entitled “Space Debris – Providing mitigation and remediation, hypervelocity Research (COSPAR) Assembly will the Scientific Foundation for Action.” impact range developments, and protection. convene in Istanbul’s Congress Center on PEDAS.1 sessions will include advances Please see the COSPAR website at https:// Saturday, 30 July 2016 and run through in ground- and space-based measurements www.cospar-assembly.org/ and the Sunday, 7 August. The COSPAR panel of the orbital debris environment, Assembly website http://cospar2016. Potentially Environmentally Detrimental and orbital debris tubitak.gov.tr/ for further information. Activities in Space (PEDAS) will conduct a environment modeling, risk assessment, 6-11 August 2016: 30th Annual AIAA/USU Conference on Small Satellites, Logan, Utah (USA) Utah State University will host the Developer’s Workshop will be conducted previews the next 18 months. Please see the 30th Annual AIAA/USU Conference on on 6-7 August. The conference program conference website at http://www.smallsat. Small Satellites at the Taggert Student considers all aspects of org/index for further information. Center in August 2016. In addition, the pre- development and deployment, and reviews conference 13th Annual Summer CubeSat the past 18 months of smallsat launches and

20-23 September 2015: 17th Advanced Maui Optical and Space Surveillance Technologies Conference, Maui, Hawaii (USA) The technical program of the are mission critical to Space Situational Imaging, Astrodynamics, Non-resolved 17th Advanced Maui Optical and Space Awareness. The technical sessions include Object Characterization, and related topics. Surveillance Technologies Conference papers and posters on Orbital Debris, Space Additional information about the conference (AMOS) will focus on subjects that Situational Awareness, Adaptive Optics & is available at http://www.amostech.com.

26-30 September 2016: 67th International Astronautical Congress, Guadalajara, Mexico The Mexican Space Agency, Agencia of Astronautics (IAA) Symposium on space situational awareness. These topics Espacial Mexicana (AEM), will host the Space Debris to address the complete will be covered in nine oral sessions and one 67th IAC Conference with a theme of spectrum of technical issues of space debris poster session. For conference information "Making space accessible and affordable measurements, modeling, risk assessments, as it is posted, visit the IAF conference to all countries." The 2016 Congress will reentry, hypervelocity impacts and webpage at http://iac2016.org. include the 14th International Academy protection, mitigation and standards, and

11 Orbital Debris Quarterly News

INTERNATIONAL SPACE MISSIONS 1 October 2015 – 31 December 2015 DAS 2.0 NOTICE

Perigee Apogee Earth Other International Country/ Inclination Attention DAS 2.0 Users: an Payloads Altitude Altitude Orbital Cataloged Designator Organization (DEG) Rocket (KM) (KM) Bodies Debris updated solar flux table is available 2015-055A PROGRESS-M 29M RUSSIA 397 408 51.6 1 0 for use with DAS 2.0. Please go to 2015-056A MORELOS 3 7 MEXICO 35779 35794 7.1 1 0 the Orbital Debris Website at http:// 2015-057A LQSAT CHINA 639 665 98.0 0 0 2015-057B LINGQIAO VIDEO A CHINA 639 665 98.0 www.orbitaldebris.jsc.nasa.gov/ 2015-057C LINGQIAO VIDEO B CHINA 638 664 98.0 2015-057D JILIN 1 CHINA 638 664 98.0 mitigate/das.html to download the 2015-058A USA 264 USA 1 1 updated table and subscribe for 2015-058B AEROCUBE 5C USA 2015-058C AEROCUBE 7 USA email alerts of future updates. 2015-058D FOX-1 USA 2015-058E BISONSAT USA 2015-058F ARC-1 USA 2015-058G SNAP-3 ALICE USA NO ELEMENTS 2015-058H LMRST-SAT USA AVAILABLE 2015-058J SNAP-3 EDDIE USA 2015-058K PROPCUBE 3 USA 2015-058L SINOD-D 1 USA UPDATE YOUR ODQN 2015-058M SNAP-3 JIMI USA 2015-058N PROPCUBE 1 USA SUBSCRIPTION 2015-058P SINOD-D 3 USA 2015-059A APSTAR 9 CHINA 35774 35799 0.0 1 0 ADDRESS 2015-060A TURKSAT 4B TURKEY 35776 35798 0.0 1 1 If you have stopped receiving email 2015-061A TIANHUI 1-03 CHINA 488 502 97.4 1 2 notification when the latest ODQN is 2015-062A NAVSTAR 75 (USA 265) USA 20158 20207 55.0 1 0 available, please update your email 2015-063A CHINASAT 2C CHINA 35778 35797 0.5 1 0 address using the ODQN Subscription 2015-064A YAOGAN 28 CHINA 467 483 97.3 1 3 2015-065A GSAT 15 35775 35798 0.0 1 1 Request Form located on the NASA 2015-065B BADR 7 ARAB SCO 35757 35798 0.0 Orbital Debris Program Office website, 2015-066A COSMOS 2510 RUSSIA 1588 38770 63.8 1 0 www.orbitaldebris.jsc.nasa.gov. This 2015-067A LAOSAT 1 LAOS 35779 35794 0.1 1 0 form can be accessed by clicking on 2015-068A 12V CANADA 35776 35798 0.1 1 0 “Quarterly News” in the Quick Links 2015-069A YAOGAN 29 CHINA 628 630 97.8 1 0 area of the website and selecting 2015-070A LISA PATHFINDER ESA SUN-EARTH LAGRANGE 1 1 0 “ODQN Subscription” from the pop-up 2015-071A COSMOS 2511 RUSSIA 88 298 98.2 2 0 2015-071B COSMOS 2512 RUSSIA 684 694 98.2 box that appears. 2015-072A CYGNUS ORB-4 USA 397 408 51.6 0 0 2015-073A CHINASAT 1C CHINA 35780 35793 0.0 1 0 2015-074A ELEKTRO-L 2 RUSSIA 35779 35793 0.3 2 7 2015-075A COSMOS 2513 RUSSIA 35776 35797 0.0 1 1 2015-076A -TMA 19M RUSSIA 397 408 51.6 1 0 Technical Editor 2015-077A VELOX C1 SINGAPORE 533 550 15.0 1 0 Phillip Anz-Meador 2015-077B KENT RIDGE 1 SINGAPORE 534 550 15.0 2015-077C ATHENOXAT 1 SINGAPORE 531 550 15.0 2015-077D TELEOS 1 SINGAPORE 535 551 15.0 Managing Editor 2015-077E GALASSIA SINGAPORE 529 549 15.0 2015-077F VELOX 2 SINGAPORE 536 551 15.0 Debi Shoots 2015-078A DAMPE CHINA 488 505 97.3 0 0 2015-079A GALILEO 12 (269) ESA 23511 23568 55.0 1 0 2015-079B GALILEO 11 (268) ESA 23552 23618 55.0 Correspondence concerning 2015-080A PROGRESS MS-01 RUSSIA 396 407 51.6 1 0 the ODQN can be sent to: 2015-081A FM 114 USA 615 658 47.0 0 0 2015-081B ORBCOMM FM 119 USA 614 658 47.0 Debi Shoots 2015-081C ORBCOMM FM 105 USA 614 657 47.0 2015-081D ORBCOMM FM 110 USA 614 657 47.0 NASA Johnson Space Center 2015-081E ORBCOMM FM 118 USA 614 657 47.0 2015-081F ORBCOMM FM 112 USA 614 657 47.0 Orbital Debris Program Office 2015-081G ORBCOMM FM 113 USA 613 655 47.0 Mail Code JE104 2015-081H ORBCOMM FM 115 USA 613 655 47.0 2015-081J ORBCOMM FM 108 USA 613 655 47.0 Houston, TX 77058 2015-081K ORBCOMM FM 117 USA 613 653 47.0 2015-081L ORBCOMM FM 116 USA 613 654 47.0 [email protected] 2015-082A EXPRESS AMU1 RUSSIA 35777 35796 0.0 1 1 2015-083A GAOFEN 4 CHINA 35780 35791 0.4 1 0

12 www.orbitaldebris.jsc.nasa.gov

INTERNATIONAL SPACE MISSIONS SATELLITE BOX SCORE (as of 6 April 2016, cataloged by the 1 January 2016 – 31 March 2016 U.S. SPACE SURVEILLANCE NETWORK)

Perigee Apogee Earth Other Rocket International Country/ Inclination Country/ Payloads Altitude Altitude Orbital Cataloged Payloads Bodies Total Designator Organization (DEG) Rocket Organization (KM) (KM) Bodies Debris & Debris 2016-001A BELINTERSAT 1 BELARUS 35780 35791 0.0 1 0 CHINA 215 3576 3791

2016-002A JASON 3 USA 1332 1344 66.0 0 0 CIS 1468 4808 6276 2016-003A IRNSS-1E INDIA 35696 35879 28.1 1 0 ESA 56 53 109 2016-004A 29E INTELSAT 35775 35798 0.1 1 0 2016-005A EUTE 9B 35779 35791 0.1 1 1 FRANCE 60 460 520

2016-067HP AGGIESAT 4 USA 394 399 51.6 0 0 INDIA 64 112 176 2016-067HQ BEVO 2 USA 391 395 51.6 0 0 JAPAN 140 75 215 2016-006A BEIDOU M3-S CHINA 21523 21532 55.0 2 0 USA 1338 4145 5483 2016-007A NAVSTAR 76 (USA 266) USA 20174 20188 55.0 1 0 2016-008A COSMOS 2514 (GLONASS) RUSSIA 19104 19156 64.8 1 0 OTHER 700 115 815 2016-009A KMS 4 N. KOREA 463 501 97.5 1 0 2016-010A USA 267 USA NO ELEMS. AVAILABLE 0 0 TOTAL 4041 13344 17385 2016-011A SENTINEL 3A ESA 802 803 98.6 1 0

2016-012A ASTRO H JAPAN 560 580 31.0 1 1 2016-012B CHUBUSAT 2 JAPAN 559 579 31.0 2016-012C CHUBUSAT 3 JAPAN 559 578 31.0 2016-012D HORYU 4 JAPAN 557 577 31.0

2016-013A SES 9 SES EN ROUTE TO GEO 1 0 Visit the NASA 2016-014A EUTE 65W EUTELSAT 35779 35794 0.1 1 0 Orbital Debris Program Office 2016-015A IRNSS 1F INDIA EN ROUTE TO GEO 5.1 1 0 2016-016A RESURS P3 RUSSIA 468 473 97.3 1 0 Website 2016-017A EXOMARS ESA EN ROUTE TO MARS 0 1 2016-018A SOYUZ-TMA 20M RUSSIA 403 406 51.6 1 0 www.orbitaldebris.jsc.nasa.gov 2016-019A CYGNUS OA-6 USA 403 406 51.6 0 0 2016-020A COSMOS 2515 RUSSIA 542 595 97.6 1 0 2016-021A BEIDOU IGSO 6 CHINA EN ROUTE TO GEO 55.0 1 0

OTHER SING This chart shows the relative proportions TURK of debris to non-debris as of January 2016. SWED 03B Debris in this case includes mission-related SAUD debris, anomalous debris, and breakup AB ARGN debris. Non-debris includes spacecraft INDO (including non-functioning spacecraft) and ISRA AUS rocket bodies. The vast majority are breakup EUME IM debris. In this chart, launching entities BRAZ debris (all types) with 10 or more objects on orbit are listed

SKOR SPN non Debris individually; those with less are lumped into IT the ‘other’ category. Launching entities SEAL include countries, international agencies or

source ORB UK consortia, and commercial organizations. GER CA International government-level partnerships EUTE include the (ESA), SES CHBZ ArabSat (AB), InMarSat (IM), the EuMetSat ITSO organization (EUME), the EuTelSat GLOB ESA organization (EUTE), and the China-Brazil IND partnership (CHBZ). Commercial concerns JPN FR include (SEAL), Orbcomm PRC US (ORB), (GLOB), SES, Other 3 CIS Billion Networks () and since 2001, 0 1000 2000 3000 4000 5000 6000 7000 Intelsat (ITSO). cataloged Earth orbiting objects Source: 6 January 2016 JSpOC boxscore.

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18000 17000 16000 15000 14000 13000 12000 11000 10000 Number of Objects of Number Monthly Number of Cataloged Objects in Earth Orbit by Object Type: This chart displays a summary of all objects in Earth orbit Monthly Number of Cataloged Objects in Earth Orbit by Object Type: officially cataloged by the U.S. Space Surveillance Network. “Fragmentation debris” includes satellite breakup debris and anomalous event debris, while “mission-related debris” includes all objects dispensed, separated, or released as part of the planned mission.

National Aeronautics and Space Administration Lyndon B. Johnson Space Center 2101 NASA Parkway Houston, TX 77058 www.nasa.gov http://orbitaldebris.jsc.nasa.gov/

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